EP1247735A2 - Procédé pour réduire les vibrations dans des cavités et agencement de surface dans un écoulement de fluide - Google Patents

Procédé pour réduire les vibrations dans des cavités et agencement de surface dans un écoulement de fluide Download PDF

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Publication number
EP1247735A2
EP1247735A2 EP02003770A EP02003770A EP1247735A2 EP 1247735 A2 EP1247735 A2 EP 1247735A2 EP 02003770 A EP02003770 A EP 02003770A EP 02003770 A EP02003770 A EP 02003770A EP 1247735 A2 EP1247735 A2 EP 1247735A2
Authority
EP
European Patent Office
Prior art keywords
flow
cavity
delta wing
longitudinal vortex
surface arrangement
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP02003770A
Other languages
German (de)
English (en)
Other versions
EP1247735A3 (fr
EP1247735B1 (fr
Inventor
Jan Dr. Ing. Delfs
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Deutsches Zentrum fuer Luft und Raumfahrt eV
Original Assignee
Deutsches Zentrum fuer Luft und Raumfahrt eV
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Deutsches Zentrum fuer Luft und Raumfahrt eV filed Critical Deutsches Zentrum fuer Luft und Raumfahrt eV
Publication of EP1247735A2 publication Critical patent/EP1247735A2/fr
Publication of EP1247735A3 publication Critical patent/EP1247735A3/fr
Application granted granted Critical
Publication of EP1247735B1 publication Critical patent/EP1247735B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
    • B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/06—Boundary layer controls by explicitly adjusting fluid flow, e.g. by using valves, variable aperture or slot areas, variable pump action or variable fluid pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C2230/00—Boundary layer controls
    • B64C2230/20—Boundary layer controls by passively inducing fluid flow, e.g. by means of a pressure difference between both ends of a slot or duct
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Definitions

  • the invention relates to a method for reducing vibrations in one Cavity, the opening of the cavity from a flow in a flow direction is overflowing.
  • the invention further relates to an overflow surface arrangement with a cavity, wherein the opening of the cavity from a flow in a flow direction can be overflowed.
  • the object of the invention was therefore to provide an improved method for reduction to indicate vibrations in a cavity that is reliable, inexpensive and is simple and as independent as possible from the technical boundary conditions and the shape of the cavity can be performed.
  • the task is accomplished by generating a longitudinal vortex pair flow with two Longitudinal vortex structures on the side edges of the cavity in the direction of flow solved, the direction of rotation of the two longitudinal vortex structures of the Longitudinal vortex pair flow opposite to each other and the two longitudinal vortex structures are directed so that the one on the right in the direction of flow
  • the longitudinal vortex structure rotates clockwise and the left in the direction of flow longitudinal vortex structure rotates counterclockwise.
  • the longitudinal vortex structures induced along the entire side edge of the cavity opening cause a destruction of the quasi two-dimensionality of the Shear layer.
  • the stability characteristic of the cavity shear layer is hereby changed and this stabilized.
  • the pair induces longitudinal vertebral structures Velocity components normal to the cavity opening in the Flow, which raise the cavity shear layer and thereby the inclination of the Reduce the cavity shear layer to interact with the cavity back.
  • the longitudinal vortex structures are also generically large-scale, stationary flow structures, which have little or no additional turbulence and unsteadiness induce so that no increase in the broadband spectrum of the pressure signals takes place in the cavity. In addition to the tonal signal components, the broadband shares also decreased.
  • the direction of rotation of the longitudinal vortex structures is directed so that the Longitudinal vortex flows cause suction from the cavity. This has quasi an air suction.
  • the longitudinal vortex structures are preferably arranged by one Delta wing generated in the area in front of the cavity seen in the flow direction.
  • the delta wing has two flow separation edges that are arrow-shaped the direction of flow converge.
  • the delta wing stretches transverse to the flow direction parallel to a flow plane through the surface the opening of the cavity is defined.
  • the stall edges run thus upstream arrow-shaped relatively pointed together. At the stall edges the flow is deflected so that it swirls in the longitudinal direction and a longitudinal vortex structure is induced in each case.
  • the arrow angle ⁇ of the delta wing between each flow separation edge and the trailing edge of the delta wing running transversely to the direction of flow should be about 70 °.
  • the angle of attack ⁇ of the delta wing between the surface of the delta wing and the flow area is preferably variable and during flight open cavity set to about 10 °.
  • the span of the delta wing downstream in the area of the opening of the Cavity should be about 1.5 times the width of the cavity. On In this way, the longitudinal vortex structures are optimal on the side edges of the Cavity induced.
  • the object of the invention was also to provide an overflowed surface arrangement specify a cavity in which the cavity vibrations are optimally reduced become.
  • the task is accomplished by a device in the area in front of the cavity in the direction of flow seen to create a longitudinal vortex pair flow with two Longitudinal vortex structures in the area of the side edges of the cavity in the direction of flow solved, wherein the two longitudinal vertebrae structures are opposite to each other running direction of rotation and in the flow direction on the right longitudinal vortex structure rotates clockwise and in the direction of flow the longitudinal vortex structure on the left rotates counterclockwise.
  • a device for adjusting the angle of attack ⁇ of the delta wing is preferred coupled to the delta wing.
  • a pivot axis may be provided, wherein the delta wing is pivotable about the pivot axis.
  • Figures 1a and 1b leave an aircraft 1 with a cavity 2 on the underside of the fuselage as a half-section in plan view (a) and in cross section (b) recognize.
  • the cavity 2 e.g. B. a weapon shaft of a fighter plane, has a length L in the direction of flow S, a depth D and a width W.
  • the flow is essentially transonic when the aircraft is moving 1 moved at a speed of about 0.8 to 1.3 mach.
  • Figure 2 shows a cavity 2 in cross section.
  • the cavity 2 is in one Surface arrangement 5 installed, which is flowed over in the flow direction S.
  • a cavity shear layer 6 is formed which is hydrodynamically unstable and consequently tends to spatially resonating wave movements. hereby immerses the cavity shear layer 6 continuously into the cavity 2 and again what is outlined by arrow 7. This is the back wall of the cavity 8 temporarily exposed to the full flow on the surface arrangement 5, which builds up on the cavity rear wall 8 and generates a pressure pulse, whose sound pressure component 9 within the cavity 2 to the cavity front wall 10 runs ahead. At the top of the cavity front wall there will be a new unstable wave in the cavity shear layer 6 excited, so that a feedback and effect of the vibration effect is effected.
  • FIG. 3 shows a perspective view of a cavity 2 with a delta wing 11 recognize that in the area in front of the cavity 2 in the flow direction S is arranged arranged.
  • the so-called delta wing 11 has a pair of stall edges that oppose it flow direction S converge arrow-shaped.
  • the top view is the delta wing 11 thus delta or triangular.
  • Cross to the direction of flow S seen, the delta wing 11 extends parallel to the flow plane, the is defined by the opening 12 of the cavity 2.
  • the longitudinal vortex structures 13a and 13b have one in opposite directions running direction of rotation, as outlined in FIG. 4, that it has a Generate suction from the cavity 2.
  • FIG. 4 shows the cavity 2 seen in cross section in the flow direction S. detect. It is clear that the longitudinal vortex structures 13a and 13b with their vortex axis each formed in the region of the side edges of the cavity 2 are.
  • the longitudinal vortex structure 13a located on the right in the flow direction S rotates clockwise and the longitudinal vortex structure on the left in flow direction S 13b rotates counterclockwise.
  • FIG. 5 shows the delta wing 11 against the flow direction S detect.
  • the rear edge of the delta wing 11 is therefore visible.
  • the delta wing 11 essentially consists of a triangular as thin as possible, but stable plate, which is located on the center axis of the delta wing 11 the cross member 14 extending into the surface arrangement is integrally connected and is connected to the surface structure via the cross member 14.
  • FIG. 6 shows the delta wing 11 in cross section, that in the area is arranged in front of the cavity 2.
  • the cross member 14 on a pivot axis 15 in the front Area of the delta wing 11 hinged to the surface structure and around Pivot axis 15 is pivotable by an angle of attack ⁇ .
  • the angle of attack ⁇ is the angle between the surface of the delta wing 11 and the flow plane set that is defined by the area of the opening of the cavity 2 is. During flight, the angle of attack ⁇ is preferably set to approximately 10 °. When the cavity 2 is closed, the delta wing 11 becomes complete retracted.
  • FIG. 7 leaves the delta wing 11, which is in the area in front of the cavity 2 and directly next to it, can be seen in the top view. It becomes clear that the cross member 14 extends along the central axis of the delta wing 11 and perpendicular to the surface of the delta wing 11 integrally connected to the delta wing 11 is. The flow separation edges run counter to the flow direction S arrow-shaped together, the wingspan of the delta wing about 1.5 times is as large as the width W of the cavity 2.
  • the arrow angle ⁇ between a flow separation edge and that across The flow direction S of the trailing edge of the delta wing 11 is approximately 70 °.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Buildings Adapted To Withstand Abnormal External Influences (AREA)
EP02003770A 2001-04-06 2002-02-20 Procédé pour réduire les oscillations dans des cavités et agencement de surface dans un écoulement de fluide Expired - Lifetime EP1247735B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE10117300A DE10117300B4 (de) 2001-04-06 2001-04-06 Verfahren zur Reduzierung von Schwingungen in einem Hohlraum und überströmte Flächenanordnung
DE10117300 2001-04-06

Publications (3)

Publication Number Publication Date
EP1247735A2 true EP1247735A2 (fr) 2002-10-09
EP1247735A3 EP1247735A3 (fr) 2004-01-28
EP1247735B1 EP1247735B1 (fr) 2005-04-20

Family

ID=7680705

Family Applications (1)

Application Number Title Priority Date Filing Date
EP02003770A Expired - Lifetime EP1247735B1 (fr) 2001-04-06 2002-02-20 Procédé pour réduire les oscillations dans des cavités et agencement de surface dans un écoulement de fluide

Country Status (3)

Country Link
EP (1) EP1247735B1 (fr)
DE (2) DE10117300B4 (fr)
ES (1) ES2237626T3 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2957052A1 (fr) * 2010-03-03 2011-09-09 Airbus Operations Sas Dispositif aerodynamique de reduction de vibrations de trappes d'un train d'atterrissage avant d'un avion.
EP3458799A4 (fr) * 2016-05-17 2019-12-18 Saab AB Distributeur de contre-mesure ayant un déflecteur variable et procédé permettant de lancer une contre-mesure
US10683092B2 (en) 2016-05-17 2020-06-16 Saab Ab Magazine and method for launching countermeasures
US10683090B2 (en) 2016-05-17 2020-06-16 Saab Ab Dynamically with tiltable magazine and method for launching countermeasures
US10684099B2 (en) 2016-05-17 2020-06-16 Saab Ab Magazine, cartridge and method for launching a countermeasure
CN112623197A (zh) * 2020-12-29 2021-04-09 中国航空工业集团公司西安飞机设计研究所 一种空腔噪声控制的分流装置及噪声控制方法
CN114735203A (zh) * 2022-06-13 2022-07-12 中国空气动力研究与发展中心高速空气动力研究所 一种三棱柱状飞行器武器舱噪声抑制装置

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102009052142B3 (de) * 2009-11-06 2011-07-14 MTU Aero Engines GmbH, 80995 Axialverdichter
CN108045555B (zh) * 2017-11-30 2021-01-19 中国航空工业集团公司沈阳飞机设计研究所 一种设置于深度开式内埋物品舱前缘的扰流板

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4174083A (en) * 1977-04-29 1979-11-13 The Boeing Company Flow deflector for fluid inlet
US4696442A (en) * 1986-07-14 1987-09-29 The Boeing Company Vortex generators for inlets
US5340054A (en) * 1991-02-20 1994-08-23 The United States Of America As Represented By The Secretary Of The Navy Suppressor of oscillations in airframe cavities
US5699981A (en) * 1996-03-18 1997-12-23 The United States Of America As Represented By The Secretary Of The Air Force Aircraft cavity acoustic resonance suppression system
US5772155A (en) * 1996-06-01 1998-06-30 Nowak; Dieter K. Aircraft wing flaps
US6206326B1 (en) * 1999-04-12 2001-03-27 The United States Of America As Represented By The Secretary Of The Air Force Method and apparatus for actively enhancing aircraft weapon separation

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2957052A1 (fr) * 2010-03-03 2011-09-09 Airbus Operations Sas Dispositif aerodynamique de reduction de vibrations de trappes d'un train d'atterrissage avant d'un avion.
EP3458799A4 (fr) * 2016-05-17 2019-12-18 Saab AB Distributeur de contre-mesure ayant un déflecteur variable et procédé permettant de lancer une contre-mesure
US10683092B2 (en) 2016-05-17 2020-06-16 Saab Ab Magazine and method for launching countermeasures
US10683090B2 (en) 2016-05-17 2020-06-16 Saab Ab Dynamically with tiltable magazine and method for launching countermeasures
US10684099B2 (en) 2016-05-17 2020-06-16 Saab Ab Magazine, cartridge and method for launching a countermeasure
US10696401B2 (en) 2016-05-17 2020-06-30 Saab Ab Countermeasure dispenser with variable spoiler and method for launching a countermeasure
US11008099B2 (en) 2016-05-17 2021-05-18 Saab Ab Device and method for firing direction limitation and a countermeasure arrangement
CN112623197A (zh) * 2020-12-29 2021-04-09 中国航空工业集团公司西安飞机设计研究所 一种空腔噪声控制的分流装置及噪声控制方法
CN112623197B (zh) * 2020-12-29 2023-08-04 中国航空工业集团公司西安飞机设计研究所 一种空腔噪声控制的分流装置及噪声控制方法
CN114735203A (zh) * 2022-06-13 2022-07-12 中国空气动力研究与发展中心高速空气动力研究所 一种三棱柱状飞行器武器舱噪声抑制装置

Also Published As

Publication number Publication date
ES2237626T3 (es) 2005-08-01
EP1247735A3 (fr) 2004-01-28
EP1247735B1 (fr) 2005-04-20
DE10117300B4 (de) 2004-04-29
DE10117300A1 (de) 2002-11-21
DE50202824D1 (de) 2005-05-25

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